The DOI matches its Crossref record; 2 of the 2 references it cites were found in a registry or an index.
Controllability of spacecraft attitude under magnetic actuation
Abstract
In this paper, we apply nonlinear controllability theory to the attitude dynamics of a magnetically actuated spacecraft in a Keplerian orbit in the geomagnetic field. The variation of the geomagnetic field along the orbit makes the dynamical equations time varying in nature. Hence we first present sufficient conditions for accessibility, strong accessibility and controllability of a general time-varying system. We apply these sufficient conditions to show that the attitude dynamics of a spacecraft actuated by three magnetic actuators and subjected to a general time-varying magnetic field are strongly accessible if the magnetic field and its first two time derivatives are linearly independent at every instant. In addition, if the magnetic field is periodic in time, then the attitude dynamics of the spacecraft are controllable. These results are used to show that the attitude dynamics of a spacecraft actuated by three magnetic actuators in a closed Keplerian orbit in a of the geomagnetic field are strongly accessible and controllable if the orbital plane contains neither the geomagnetic equator nor the geomagnetic poles.
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Citations
Cites
Nonlinear controllability and observability
Hermann, R., & Krener, A. (1977) · IEEE Transactions on Automatic Control · doi:10.1109/tac.1977.1101601 · Cited by 2,374
Spacecraft Attitude Determination and Control
(1978) · Astrophysics and Space Science Library · doi:10.1007/978-94-009-9907-7 · Cited by 1,892
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Cited by
Sorted by citations
3CAT-2: Attitude Determination and Control System for a GNSS-R Earth Observation 6U CubeSat Mission
Cortiella, A., Vidal, D., Jané, J., Juan, E., Olivé, R., Amézaga, A., Munoz, J. F., Carreno-Luengo, P. V. H., & Camps, A. (2016) · European Journal of Remote Sensing · doi:10.5721/eujrs20164940 · Cited by 23
“Fortunately, as extensively studied in [Bhat and Dham, 2003], as long as the orbital plane does not coincide with the geomagnetic equatorial plane and does not contain the magnetic poles - this mission has an orbit inclination of ~98º-, the spacecraft is controllable on average throughout one…”
Background
Metadata
- Authors
- Bhat, S. P., & Dham, A. S.
- Affiliations
- Indian Institute of Technology Bombay (IN)
- Indian Air Force (IN)
- ORCID
- Bhat, S.P.
- Venue
- 42nd IEEE International Conference on Decision and Control (IEEE Cat. No.03CH37475)
- Publisher
- IEEE
- Published
- 2004-07-08
- Volume
- 3
- Pages
- 2383-2388
- ISSN
- 0191-2216 (ISSN-L)
- OpenAlex
- W1563940880
- Cited by
- 28
- References
- 2
- Citations by year
- 2023: 7 · 2022: 3 · 2019: 3 · 2017: 2 · 2016: 2 · 2014: 2 · 2013: 1 · 2012: 3
- FWCI
- 1.05
- Type
- conference paper
- Language
- en
- Open access
- closed
- Locations
- IEEE Conference on Decision and Control (CDC) (publishedVersion)
- DSpace (IIT Bombay) (submittedVersion)
- Topics
- Physical Sciences › Engineering › Aerospace Engineering › Spacecraft Dynamics and Control
- Physical Sciences › Engineering › Control and Systems Engineering › Control and Stability of Dynamical Systems
- Physical Sciences › Engineering › Aerospace Engineering › Space Satellite Systems and Control
- Keywords
- spacecraft attitude control, magnetic actuators, nonlinear controllability, time-varying systems, geomagnetic field, Keplerian orbits, periodic magnetic field, sufficient controllability conditions
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